20.5x14EPN (205x14EPN.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 1.2500 14.0000 0.0000 0.0000 0.6250 0.0000 0.2960 0.0000 0.3700 0.0000 0.1200 0.0000 0.0000 0.2665 1.1752 14.0000 0.0412 -0.6812 0.6155 0.0213 0.2945 1.4099 0.3461 0.3809 0.1381 0.0246 -0.0498 0.5330 1.1156 14.0000 0.3215 -1.1948 0.6128 0.0781 0.2901 5.4841 0.3237 0.3733 0.1852 0.0572 -0.0230 0.7995 1.0810 14.0000 1.0457 -1.1936 0.6160 0.1610 0.2828 11.7596 0.3057 0.3577 0.2535 0.0918 0.0190 1.0660 1.0808 14.0000 2.3477 -0.4104 0.6239 0.2608 0.2725 19.3165 0.2945 0.3376 0.3363 0.1257 0.0726 1.3325 1.1178 14.0000 4.2470 1.2768 0.6357 0.3684 0.2593 26.8971 0.2898 0.3157 0.4263 0.1569 0.1336 1.5990 1.1861 14.0000 6.6156 3.7869 0.6501 0.4746 0.2431 33.3641 0.2884 0.2937 0.5163 0.1835 0.1976 1.8655 1.2735 14.0000 9.1746 6.7578 0.6661 0.5701 0.2240 38.0515 0.2853 0.2725 0.5990 0.2037 0.2591 2.1320 1.3657 14.0000 11.5333 9.5718 0.6828 0.6459 0.2020 40.7274 0.2758 0.2522 0.6666 0.2155 0.3118 2.3985 1.4501 14.0000 13.2650 11.7832 0.6990 0.6928 0.1770 41.3547 0.2567 0.2328 0.7093 0.2160 0.3475 2.6650 1.5182 14.0000 13.9936 12.9720 0.7137 0.7015 0.1491 39.8856 0.2263 0.2139 0.7173 0.2003 0.3561 2.9298 1.5697 14.0000 14.0000 13.3389 0.7251 0.6832 0.1248 37.2533 0.1959 0.1990 0.7014 0.1720 0.3443 3.1662 1.6056 14.0000 14.0000 13.4038 0.7317 0.6652 0.1190 35.1355 0.1911 0.2030 0.6870 0.1492 0.3353 3.4009 1.6321 14.0000 14.0000 13.4178 0.7350 0.6471 0.1166 33.2318 0.1902 0.2091 0.6726 0.1280 0.3276 3.6356 1.6502 14.0000 14.0000 13.4303 0.7351 0.6291 0.1142 31.5033 0.1885 0.2132 0.6583 0.1079 0.3208 3.8703 1.6602 14.0000 14.0000 13.4389 0.7322 0.6114 0.1120 29.9297 0.1860 0.2153 0.6439 0.0888 0.3150 4.1049 1.6626 14.0000 14.0000 13.4403 0.7266 0.5941 0.1100 28.4931 0.1828 0.2155 0.6296 0.0709 0.3101 4.3396 1.6579 14.0000 14.0000 13.4272 0.7182 0.5772 0.1080 27.1780 0.1791 0.2140 0.6153 0.0543 0.3060 4.5743 1.6465 14.0000 14.0000 13.4106 0.7073 0.5607 0.1062 25.9709 0.1748 0.2106 0.6011 0.0391 0.3027 4.8090 1.6288 14.0000 14.0000 13.3926 0.6940 0.5446 0.1045 24.8598 0.1702 0.2055 0.5868 0.0251 0.3000 5.0437 1.6053 14.0000 14.0000 13.3745 0.6784 0.5289 0.1029 23.8345 0.1652 0.1989 0.5726 0.0125 0.2979 5.2784 1.5764 14.0000 14.0000 13.3560 0.6607 0.5136 0.1014 22.8861 0.1599 0.1909 0.5584 0.0012 0.2963 5.5131 1.5427 14.0000 14.0000 13.3391 0.6411 0.4988 0.1001 22.0066 0.1544 0.1817 0.5443 -0.0089 0.2951 5.7478 1.5044 14.0000 14.0000 13.3237 0.6196 0.4844 0.0989 21.1892 0.1488 0.1716 0.5301 -0.0179 0.2943 5.9825 1.4622 14.0000 14.0000 13.3095 0.5964 0.4703 0.0978 20.4278 0.1430 0.1608 0.5159 -0.0260 0.2936 6.2172 1.4164 14.0000 14.0000 13.2947 0.5718 0.4564 0.0969 19.7172 0.1372 0.1498 0.5017 -0.0336 0.2926 6.4518 1.3675 14.0000 14.0000 13.2773 0.5457 0.4428 0.0960 19.0525 0.1313 0.1388 0.4875 -0.0409 0.2912 6.6865 1.3159 14.0000 14.0000 13.2563 0.5184 0.4293 0.0953 18.4297 0.1255 0.1278 0.4732 -0.0478 0.2894 6.9212 1.2621 14.0000 14.0000 13.2345 0.4899 0.4160 0.0948 17.8451 0.1196 0.1170 0.4589 -0.0546 0.2872 7.1559 1.2066 14.0000 14.0000 13.2117 0.4606 0.4028 0.0943 17.2953 0.1138 0.1066 0.4447 -0.0613 0.2845 7.3906 1.1497 14.0000 14.0000 13.1877 0.4304 0.3897 0.0940 16.7774 0.1080 0.0965 0.4304 -0.0679 0.2815 7.6253 1.0919 14.0000 14.0000 13.1627 0.3995 0.3768 0.0938 16.2888 0.1024 0.0869 0.4162 -0.0747 0.2779 7.8600 1.0338 14.0000 14.0000 13.1365 0.3681 0.3639 0.0937 15.8271 0.0968 0.0779 0.4019 -0.0815 0.2738 8.0947 0.9756 14.0000 14.0000 13.1089 0.3363 0.3511 0.0937 15.3903 0.0914 0.0694 0.3877 -0.0887 0.2693 8.3294 0.9180 14.0000 14.0000 13.0799 0.3043 0.3383 0.0939 14.9764 0.0862 0.0615 0.3734 -0.0960 0.2642 8.5641 0.8612 14.0000 14.0000 13.0492 0.2722 0.3256 0.0942 14.5837 0.0811 0.0542 0.3591 -0.1038 0.2587 8.7987 0.8059 14.0000 14.0000 13.0165 0.2401 0.3129 0.0946 14.2107 0.0762 0.0476 0.3449 -0.1120 0.2526 9.0334 0.7523 14.0000 14.0000 12.9817 0.2083 0.3002 0.0951 13.8559 0.0716 0.0417 0.3306 -0.1206 0.2459 9.2681 0.7011 14.0000 14.0000 12.9444 0.1768 0.2875 0.0958 13.5181 0.0672 0.0364 0.3164 -0.1299 0.2387 9.5028 0.6525 14.0000 14.0000 12.9042 0.1457 0.2747 0.0966 13.1960 0.0630 0.0317 0.3021 -0.1397 0.2310 9.7280 0.6089 14.0000 14.0000 12.8624 0.1165 0.2624 0.0975 12.9009 0.0594 0.0277 0.2884 -0.1498 0.2230 9.7893 0.5976 13.9870 13.9871 12.8313 0.1087 0.2590 0.0977 12.8114 0.0584 0.0268 0.2846 -0.1527 0.2206 9.8410 0.5882 13.9304 13.9304 12.7368 0.1021 0.2561 0.0980 12.6962 0.0576 0.0260 0.2811 -0.1552 0.2184 9.8928 0.5754 13.8287 13.8287 12.5720 0.0920 0.2523 0.0982 12.5426 0.0565 0.0249 0.2764 -0.1597 0.2154 9.9446 0.5554 13.6820 13.6820 12.3350 0.0747 0.2469 0.0984 12.3511 0.0547 0.0232 0.2696 -0.1683 0.2110 9.9963 0.5271 13.4903 13.4903 12.0252 0.0492 0.2398 0.0987 12.1220 0.0520 0.0210 0.2606 -0.1816 0.2053 10.0481 0.4885 13.2535 13.2535 11.3135 0.0134 0.2307 0.0989 11.8557 0.0483 0.0180 0.2490 -0.2006 0.1981 10.0999 0.4357 12.9717 12.9717 10.4297 -0.0366 0.2190 0.0992 11.5527 0.0432 0.0144 0.2344 -0.2276 0.1892 10.1516 0.3578 12.6449 12.6449 9.4310 -0.1114 0.2028 0.0994 11.2132 0.0356 0.0097 0.2147 -0.2685 0.1777 10.2034 0.2038 12.2731 12.2731 8.4778 -0.2613 0.1732 0.0997 10.8375 0.0203 0.0032 0.1795 -0.3512 0.1584 10.2500 0.0261 11.9000 11.9493 11.9493 -0.4352 0.1411 0.1000 10.5112 0.0026 0.0000 0.1411 0.0000 0.0000 RADIUS: 10.25 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.66 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.222913 TOTAL WEIGHT (Kg) = 0.101094 TOTAL VOLUME (IN**3) = 3.631529 TOTAL PROJECTED AREA (IN**2) = 22.8842 MOMENT OF INERTIA (SNAIL-IN**2) = 0.010377 MOMENT OF INERTIA (Kg-M**2) = 0.001172 STATIC MOMENT, ONE SIDE (IN-LB) = 0.383518 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 71.531 INNER LIMIT (NORMALIZED BY RADIUS) = 0.061 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5523.54 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.95, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.80, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412